Equilibrating mechanism for flying machines



E. E. WINKLEY EQUILIBRAT ING MECHANISM FOR FLYISIG MACHINES April 7, 1925.

Filed Jufie 25 1918 "-5 sheets sheet 1- April 7, 1925. 1,532,616

' E. E. WINKLEY i squlmsmiwme MECHANISM F611 FLYING MACHINES Filed June 25 1918 5 Sheets-Sheet 2 I I I I l I Irvvewo r;

pril 7, 1925.

E. E. WINKLEY EQUILIBRATING MECHANISM FOR FLYING MACHINES kw; .QQ Q

April 7, 1925-. I

. E. E. WINKLEY EQUILIBRATING MECHANISM FQR FLY IN G MCHINES Fi led June 25, '1918 s Sheets-Sheet 4 April 7, 1925.

t a. E. WINKLEY EQUILIBRATINQ uacnmismroa FLYING MACHINES Filed June 25,1915 S'Sheets-Sheet s v The present invention relates to Patented Apr. 7, 1925. I I

UNITED. stares PATENT- oFFica.

,naasros n. wInKLEY, or LYNN, massacn'tisnr'rs.

nduxmnnarme mnc'nanxsm ron Fume macnmns.

- "a lication ma lime 25, 1918. Serial'No. 241,860.

To all whom it may concern.

Be it known that I, Enasros E. WINK- LEY, a citizen of theUnited States, residing at. Lynn, in the county of Essex and State of Massachusetts, have invented certain new and useful Improvements in'Equilibrating Mechanism for Flyin such as will enable t to which it appertains same.-.

ers skilled in the art machines, and more particularly to .equilibrating i'nechanisms for maintainin members or devices in a condition of's'u stantial equilibrium.

The invention scribed for the sake of concreteness in 'c'0nnection with a flying machine. It will be clear, however, that the invention is of broader applicability than to flying ma; chines alone and that any one of many other types of machines might havebeen chosen equally well for illustrative purposes. The operation of machines in and of equilibratmg mechanisms in particular, is defective in that the moving parts do not respond readil to the action of the op,- erative forces.

Tiis is'caused by a sluggishness of act-ion due to well known, inher- I of the heavy out time las. Thus, it has been proposed to control oth the longitudinal an the lateral equilibrium or stability of a flying machine that or lateral rethe guiding devices of the when either the longitudinal lation between the devices to restore the machine to itsnormal condition of equilibrium. A practical objection to the'employment of a pendulum directly connected with the guiding devices of a .fl ing machine lies in the fact that .the penduum cannot act upon the guidingde- Vices to turn the latter to restore the machine to its normal condition until the angular relation between the pendulum and the flying machine is of the fact that the body, thereby exerting considerable friction upon its bearing,

guiding devices requires that a considerab amount of power be exerted, the

Machines; and I do hereby declare the fo lowing to be a full, clear, and exact description of the invention,

to make and usethe wiu be hereinafter dc I l genera elapsed.

connected with pendulum and the flyingmachine is changed by a tipping of the machine, the pendulum acts upon the guiding the guidin independent changed. By reason pendulum is a relatively and the turning-scribed, an e tendency of the pendulum is tomove with the flyingmachine and remain infixed an-- gular relation therewith, so-that an appreciable period of time elapses before gravity, in acting upon the pendulum, can bring its yertical. axis perpendicular, thereby changmg the angular relation between the vertical axis of the pendulum and either the longitudinal or lateral axis of the H ing machine. This time interval or lag is resent not only whenthe equilibrium of e machine is controlled by a spective of the nature of the controlling mechanism, If the machine be controlled, not by a pendulum, but by pneumatically operating devices, for example, the time lag will be caused by the lap of the valves. 11' the machine is controlled by a clutch, the time lag will be found during the period when the clutch parts are moved relatively toward each other into operative Puringthis time interval or mg devices, of course, do not actupon the machine, so that thereis no actual restormg movement of the machine toward e uilibrium until The result is that when the equihbrium or stability of the flying machine is disturbed either longitudinally or laterally, its tendency is to tip still farther in either direction. The 111 that the flying machine pursues an undulatpendulum, but irre relation. lag, the guid-' timate result is. either i a in course or else that it is completely'overba anced and falls. I

It is, therefore,- an object of the present invention to reduce the time la 5 incident to the operation of machines, an particularly those incident to the operation of equililoratingmechanisms.

To the attainment of this end a feature of the invention resides in initially moving devices in response to' a force of the normal restoring force and which acts before the normal force can act. 2 By the time that the normal restoringforce commences to act, therefore, 1 some.

force has already been exerted upon the machine to compensate for the time interval or lag during which the normal restoring means is initially ineffective. In the specific'embodiment of the invention, which -is herein illustrated and deuilibrating mechanism is provided for a ying machine in which a relatively heavy pendulum 'is used to act upon which the guiding1 the giiiding devices to restore the flying machine to its condition of equilibrium, and an auxiliary pendulum, which is of relatively light weight, is emplo ed to perform no other function than to tirow other dcvices into operation to eifect an immediate or primary restoring movement of the guiding devices. This primary movement of the uiding devices acts to part ally restore the flying machine to its COIldltlOIl of equilibrium, thus compensating for the time lag of the heavy pendulum. Incidentally, the auxiliary endulum serves to conneet the main pen ulum with the guiding devices, so that in case the flying machme 1s u nbal anced a substantial amount, the guiding devices will be turned accordingly to effect a greater restoring tendency thanwhen they are first turned throu h the medium of the auxiliary pendulum a one.

By reason of the fact that the pendulum for controlling the guiding devices is a relati rely heavy body and is mounted to sw ng freely, its inertia prevents it from mov ng forwardly simultaneously with the flying machine when the machine is getting under way. This results in a chan e 1n the angular relation between the pen alum and the flying machine so that the guiding devices are acted upon at a time when they should not be moved, namely; when the fl mg machine is proceeding upon a leve course. Another object of the present invention is to rovide an equilibrating mechan sm, 111 devices are controlled by a )endulum, wit a device which acts to hold the pendulum relatively immoyable with respect to the flying machine until the flying machine attains ;a predetermined speed, whereu )on the device is disconnected from the penc ulum to permit the latter to swing freely.

These objects of the invention and such other objects as are incidental thereto are cn'ibodierl in the equilibrating mechanism for flying machines hereinafter described and particularly pointed out in the appended claims.

The invention is illustrated 1n the accompanying drawings in which F igure 1 is a' diagrammatic vertical longitud nal section of the fuselage of a flying machine show ng the application thereto of the equlhbratmg mechanism; Fig. 2 is a section taken on the line 2-2 of Fig. '1; Fig. 3 is a. view similar to Fig. 1 showing the action of the auxiliary pendulum u on the horizontal rudder when the longitu inal stability of the maclnne has been disturbed; Fig. 4 is a top plan of the parts shown in the preceding figures; Fig. 5 is a view similar to Fig. 3 showing the position of the parts when the longitudinal stability of the flyin machine has been disturbed to a considerable! extent; Fig. 6 is arear elevation partly in section usual horizontal rudder,

of a flying machine showing the control of the lateral rudders or ailerons by the equilibratin mechanism and showing also the device tor holdin the at the beginning of the fligit of the ma chine; Fig. 7 is a horizontal section between the wing planes of Fig. 6, with the central portion of the lower plane broken awa ig. 8 is a detail perspective of one of t e levers for operating the ailerons' Fig. 9 is a vertical longitudinal section through the middle of the parts shown in Figs. 6 and 7 Fig. 10 is a perspective of the main pendulum and associated parts showing the manner of mounting them; Fig. 11 is a group detail perspective of certain of the parts shown in Fig. 10; Figs. 12 and 13 are respectively a. transverse and a longitudinal vertical section of the parts shown in Fig. 10; and Fig. 14:is a. diagrammatic view showing the main pendulum as a bomb filled with explosive mixture and projectiles and connected with a. detonating mechanism.

The equilibrating mechanism of the present invention as illustrated in the accompanying drawin s is adapted to control the ongitudinal stability of the flyin ma chine to which it is applied through the and the lateral stability of the flying machine through the "usual lateral rudders or ailerons. For

convenience of illustration and also of description, the e uilibratin mechanism will first be describ in its con rol upon the longitudinal stability of the flying machine and then in its control upon the lateral stabilit of the flying machine; after which it will he pointed out how the main pendulum is adapted to serve as a bomb or chamher for containing a charge of explosive mixture, which when the flying machine has reached a predetermined point is discharged by a detonating mechanism.

Referring particularl to Figs. 1 to 5 inclusive, it will be seen t iat the equilihrating mechanism is provided with a main pendulum 15 which is mounted 1' or swinging movements longitudinally or in fore and aft directions on a pivot pin 17 fired in the fuselage 18 of the flying machine. The longitudinal equilibrium or stability of the flying machine is controlled through the usual horizontally disposed rudder or guiding device 19 pivoted on the transverse, pin 20 at the rear of the machine. Depending downwardly from the rudder l9 and in fixed relationtherewith is an arm 21, pivoted to the lower end of which is a link or rod 22 pivotally connected at 'its forward end with the upright arm 24 of a three-arm lever 25 mounted to turn on a transverse pivot pin 23. The lever 25 and the rod 22 constitute guiding device operating means. On the outer end of the rear horizontal arm 26 of the lever 25 is fixed an armature 27 and on endulum fast change the an I pendulum an the machine.- The auxiliary draws the arm' 28 toward t machine. I chine is depressed, then the auxiliaryvpenduthe'outer end the front horizontal arm n28 of the lever is fixed anarmature '29,

Turning movements are imparted to the,

lever 25 to actuate the'rudder 19-to effect a change in the angle of. flightof the flying machine, when the armatures 27 and 29 are acted upon by the magnets on solenoids 30 and 31 which are supported 'respectivel on shelves and 41 protecting laterally mm the endulum 15.v T gize by a'battery 32. The battery 32 is permitted to energize either magnet when either'of two normally open circuits connect- 'ing the battery withthe magnets is closed by an auxiliary pendulum 16 making a contact with either the terminal 34 or the terminal 35. This occurs when the longitudh; nal stability of the flying machine has been disturbed by a depression of either the front or the rear end of the machine, so as to ar relation of the auxiliary pendulum 16 is mountedfor swinging movements in fore and aft directions on the pivot pin 37 fixedin the fuselage of the flyingmachine.- When the rear end of the flying machine is depressed, as shown in Fig. 3, the

auxiliary pendulum makes a contact with the terminal 35, thereby closing the circuit 38 and energizing the .mag'lnet 31. This e magnet 31, turns the lever 25 anti-clockwise" and so swings the horizontal rudder 19 in a direction'to decrease the an le of incidence of the When the i ront end of the malum contacts with the terminal 34, closing the circuit 39 and thereby energizing the.

magnet 30 to pull the arm 26 toward itself.

'.This turns the lever 25 clockwise and so swings the rudder 19 in adirectionto'lift the nose of the machine. Until the longitudinal equilibrium or stability of themaichine has beendisturbed sufliciently to cause the auxiliary pendulum to contact with either terminal 34 or 35, the main pendulumis mechanically disconnected from the horizontal rudder 19 and has no effect uponit'. When however the flying machine has been tipped longitudinally suliiciently to cause the auxiliary pendulum to contact witheither terminal, then the main pendulum is I mechanically connected with therudder 19 7 through the armature arms 26 and 28 so .that it will thereafter control the amount of movement to be imparted to the rudder 19 to restore the machine to its normal conditionof ion 'tudinal equilibrium. The movement of t e rudder 19. is roportionate to the amount the flying machine is tipped, that is to say, it is proportionate to' the amount of angular change between the pendulum and the flying ,machine. This is made clear from a consideration of Fig. 5 where the circle in dot and dash lines repree magnets are ener-- .end, t

dulum 'with-rcspectgto the fuselage of the =flying' machine, and the circle in cross section rep' dulum naturally assumes with its vertical axis perpendicular to the horizon after themachine has been ti ped for an a' reciable amountcf time. e main peml idum and the horizontal arm 28' of the three-armed lever 25 being rigidly connected through the magnet 31, the rudder 19 is, of course, turned proportionately change between the vertical axis of the mam Eendulum and the longitudinal axis of the ymg machine; If the bow of the machine sents the normal position of the main penresents the position the main pcn-. 4

to the amount of angular were depressed rather than the rear portion thereof, the rudder 19 would be turned in a reverse directlon, that is, it would be turned to a negative and not to a positive angle,

because of the fact that the auxiliary end'ulum would then be in contact with t e terminal 34 and the arm 26 of'the lever 25 would then be in contact with the magnet 30.

.Owing to the relative] great weight of the main pendulum, the riction necessarily thereby imposed uponthe pivot pin 17 and the amount of force necessaryto turn' the rudder 19, the main pendulum will not remain with its vertical'axi's per ndi'cular swin rearwardly and upwardly; in other wor the pendulum tends to maintain a fixed angular relation with the flying imachine; This has been demonstrated a series of experiments. -()f course, when the main pendulum swings in either direction with the-upward movement of either the fore or aft part of the flying machine, gravity immediatel .actsupon the pendulum so as to restore th gravity upon the main pendulum that causes the horizontal rudder'to turn in a direction a vertical axis thereof in a perpendicular position. It. is this pull of to restore the flying machine to its longitudinal equilibrium. If the amountof dis.- turbance of the flying machine is not very the rudder is not acted upon immediately by the'pendulum to restorethe equilibrium of the flying machine. If, however, the amount of disturbance is considerable, it

may be a very serious matter that the rod der is not acted upon immediately by ,the pendulum to tend to right the flying machine. To secure an immediate or primary great, it may .not be a serious matter that restori g movement of the rudder, thus compensat ng for the time lag of the main to change its an librium by means or upri ht 57 pendulum, the auxiliary rudders for controlling pendulum is provided 'to met through intermediary devices to immediately turn the rudder in a direction to'tend to restore the equilibrium of the machine upon a disturbance thereof. This auxilliary endulum is never at an time mechanical y connected with the ru der and so the amount ,of friction on the ivot pin on which the auxiliary pendulum iiangs is, therefore, reduced accordingly, the auxiliary pendulum is free lar relation with the flying machine until t 1e auxiliary pendulum contacts with either terminal 34 or 35.

The control of the lateral equilibrium or stability of the flying machine by the e uilibrating mechanism is most fully illustrated in Figs. 6 to 9 inclusive. As in the case of the control of the longitudinal equilibrium of the flying machine, the auxiliary pendu lum is employed to effect a primary restorguiding-devices or the lateral stability of the machine, and thereafter the main pendulum efiects the requisite turning movement of the lateral rudders to restore the machine to its condition of lateral equilibrium or stabilitg'. These lateral rudders or ailerons of t e flying machine are attached to the outer rearedges of the sustaining wing planes 45 and '46 of the ma chine and comprise two upper ailerons 47 and 48 pivoted -to the upper wing plane 45 and two lower ailerons 49. and 50 pivoted to the lower wing plane 46. The upper and lower ailerons are joined to ether to move in unison by means of vertically disposed rods 52. The ailerons are moved so as to restore the flying machine to lateral equiof transversely disposed rods53 and 54'. Thei its left hand end with an'arm 55 of a three-armed lever 56 pivoted .on a standard fixed on the left hand end of the ower wing plane 46, and is connected at its-right hand end with the arm 58 of a three-armed lever 59 pivoted on a standard or upright 60 fixed on the right hand end of the lower wing plane. The rod 54 is connected-at its left land end with the arm 62 ofthe lever 56 and isconnected at its right hand "en(L ;wi-th the arm 63 of mg movement of the the. lever 59. Thethi'rd arm 64 0f the lever; 56 is connected by. a universal joint with a link 65 pivotallyconnec'ted with the upright 67 fixed in the aileron 49. The third arm 68 of the lever 59 is -connected by a universal joint with a link '69 pivotally connected at its other end with an upright 70 fixed in the aileron 50. It will be observed that the arm 64 lies to the rightlnmd of the pivot point of the lever 56 and that the arm 68 lies to the left hand of the-pivot point of the lever 59.

. 48 and rod 53 is connected at "respectively upon the inseam The reason for this is movements are imparted to the levers 56 .and 59 through the rod 53, the arms-64 and the evers 56 and 59 swing. It will now be so clear that if the rod 53 is moved in a right hand direction to impart a clockwise turning movement to the overs 56 and 59, thereby moving the arm 64 arm 68 forwardly, th will be presented at a positive angle and the ailerons 48 and 50 will be presented at a negative angle. This will effect a lifting of the left hand end of the flying machine and rearwardly and the a depressing of the ri ht hand end thereof. 90

If the rod 53 is mov tron, the anti-clockwise movements im arted to the levers 56 and 59 will turn the ailerons 47 and 49 to negative anglesand the ailerons- 50 to positive angles. ailerons 49 and 50 turn both up and down the angular relation of the arms: 64 and 68 change with respect to the other two arms of the levers 56 and 59.

The lateral movements the rod 53 by the equilibrating. mechanism in the same manner that the longitudinal movements are imparted to the rod or link 22. For this purpose an auxiliary pendulum 72 fuselage of the swing laterally.

in a left hand direcflying machine so as to When the lateral equilibrium of the flying machine is disturbed, the

6) which arecarried by horizontal shelves 5 83 and 84 respectively, fixed to the main pendulum 15. The magnets 81 and 82 actarmatures 85 and 86 carried by the horizontally disposedarins of a' three-armed lever 87 The vertically disposed arm armed lever 87 is bifurcated so as to straddle a collar 90 rod 53. The bifurcated end is provided with two rolls 91 gaged by'a groove 92 formed in the collar 90 so that there may be a relative movement between the arm 89 and the collar :90 as the rod 53 is moved laterally by the swinging movements of the arm 89 of the three-- at its upper and fastened to the" of the arm 89 t when turning with which they are 70 clock-' 76 are jointed e ailerons 47 and 49 85 As the as are imparted to (Fig. 9) is mounted at 73 on the (Fig. 7) or the terminal 75 n pivoted at 88.

which are en- 89. When the'left 1.30

hand end of the flying machine, as seen in the drawings, is depressed, the auxiliary pendulum contacts with the terminal 75 and this results in an energization of the magnet 82 so that the armature 86 is pulled toward it thereby imparting a movement to the lever 87 in a cloclnvise direction to move the rod 53 in a right hand direction. The right hand movement of the rod 53 effects, as before explained, the turning of the ailerons 47 and 49 to a positive angle and of the ailerons 48 and 50 to a negative angle. The pivot oint 88. about which the lever 87 turns is he pivot point about which the-main pendulum 15 swings laterally relatively to the flying machine. When either armature 85 or 86 is drawn toward its respective magnet, the main pendulum is thereby ri idly connected with the lever 87 so that wien after the flying machine has tilted sidewise the main pendulum has had time to assume its vertical position, the ailerons will be turned pro portionately to the change in the angular the turning relation between the vertical axis of the' 'main pendulum and the lateral-axis of the flying machine. The circle in dot and dash lines in Fig. 6 indicates the position that the main pendulum is seeking to attain. Inasmuch as the lever 87 is rigidly con nected with the main pendulum through the magnet 82, a. movement in a right hand direction is bein imparted to the rod 5-) by the main pen ulum to turn the ailerons 47 and 49 to a still greater positive angle and the ailerons 48 and 50 to a still greater negative angle. As the machine rights itself laterally in response to the positions of the ailerons, the rod 53 will be moved in a left hand direction because then the main pendulum 15 will move toward the position indicated by the larger dotted circle. If the right hand end side of the flying machine is depressed, the movements'of the parts will be the reverse of what they are when the left hand side of the machine is depressed. In this case the auxiliary pendulum by contacting with the terminal 84 causes the energization of the magnet 81 so that the armature 85 will be drawn toward it to move the rod 53 in a. left'hand direction, thereby moving the ailerons 47 and 49 to he presented at a negiative angle and the ailerons 48 and 50 to e presented at a positlve angle. For the sake of convenience of illustration, the auxiliary pendulum 72 for controlling the lateral equilibrium of the machine and the auxiliary pendulum 16 for controlling the lon itudinal equilibrium of the machine have een shown as separate members. It will be understood, however, that only'one auxiliary pendulum is necessary to make and break the contacts with the four terminals. In this case it would swing from two axes disposed at right the lever 25. The

angles to each other, one axis being longitudinal and the other lateral.

Inasmuch as the main pendulum 15 serves to actuate both the horizontal rudder 19 by which the longitudinal stability of the fiyin machine is controlled and also the latera rudders or ailerons by which the lateral stabilit of the machine is controlled, the main pend iilum is mounted to have a fore and aft and a lateral swingin movement. In order that the main pendu um may swing freely in these directions it may conveniently be mounted in gimbal rings in the same mannor that a mariners compass is mounted.

This manner of mounting the main pendulum is shown particularly in Figs. 10 to 13 inclusive. The gimbal ring 95 is provided with trunnions 96 which are adapted to be received in bearings or journals fixed in the fuselage of the flying machine. Disposed at right angles to t e axis of the trunnions 96 is a stud 97 fixed in standards rising from the gimbal ring 95. The main pendulum is provided with upright ears 98 in the upper ends of which are holes 99 to fit loosely on the stud 97. With this construction it will be clear that when the flyingmachine is tip ed longitudinall the mam pendulum an the gimbal ring 95 will turn about the trunnion 96 as a pivot point relatively to the tends to remain in its normal position with its vertical axis erpendicular and the flying machine whic turns about the trunnion 96 relatively to the pendulum. On the other hand, when the flying machine is tipped laterally the gimbal rmg 95 moves with the flying machine and in this case the pendulum swings on the longitudinal stud 97 or rather the vertical axis of the pendulum tends to remain on a perpendicular dropped from the stud 97, and the flying machine tips laterally about the stud 97 The connections between the main pendulum and the horizontal rudder 19 on the one hand and the main'pendulum and the ailerons on the other hand .are shown more or less diagrammatically in Fi s. 1 to 9, to illustrate the manner in Wlllfil the auxiliary pendulum and the main pendulum act upon the guiding devices. Figs. 10 to 13 show more full the construction by which the main pen ulum isenabled to act upon the guiding devices. The horizontal arms 26 and 28 of the three-armed lever 25 are revided with depending bosses 101 in wiich the pivot pin 23 is held fast. The forward end of the rod 22 is loosely connected with a pin 102 (Fig. 13) which passes through the upper end of the bifurcated arm 24 of pivot pin 23 is loosely received in holes in t e upper ends of the lugs 103 and 104 rising respectively from the horizontal arms 83and 84 which carry the magnets 81 and 82 The arms 83 and 84 are held in fixed relation with the main pendulum by pins 106 which pass through registering holes in the ears 98 and in the uprights 107 rising from the arms 83 andv 84. T e upper ends of the uprights 107 loosely embrace the stud 97. The three-armed lever 87 pivots on the stud 97.

When the flying machine is started in flight, it usually runs along the ground until it attains the requisite speed for risin into the air. The weight of the main pendulum is such that upon the starting up of the flying machine its inertia will, of course, tend to maintain it in its original position and, therefore, the angular relation between the main pendulum and the flying machine will be changed so that the rear magnet will strike its armature and thereby tilt the three-armed lever 25 to im art a turning movement to the rudder 19 in a direction to depress the nose of the machine. In order'to obviatethis premature depressing of the machine,

while the machine is in flight, by concen-- tratlng the weight of the heavier parts ofthe machine as near to the center of gravity as possible. The explosive mixture and projectiles are indicated as contained within the main pendulum in Figs. 6, 9 and 14. When the flying machine has reached its destination or has been in flight for a predetermined length of time, the charge of explosive mixture may conveniently be detonatql by any usual or preferred term of .detonating mechanism, one form of which is diagrammatically illustrated at 121 in Fig. 14. The detonating mechanism 121 is the main endulum is held in fixed relation/in a circuit 122 which is normally 0 en.

with the yin machine as it starts in flight and until 1t a tains a redetermined s ed. This is accomplished. means of a atch 113 of the latch 110 enters a transverse recess 114 formed'in the bottom of the main pendulum. A spring 116 tends to disengage the latch from the recess 114. The latch 15 held in the recess 114 by a spring-pressed finger 117 pivoted on the axle 11 and in fixed relation with a downwardly depending board 118 which is provided with hubs 119 loosely mounted on the axle 111. The construction and arrangement of these parts is such that until the flying machine attains the predetermined speed, the latch 110 is held in the recess 1'14 and the main endulum is thereby held fixed relation with the flying machine, but when the flying machine attains a predetermined speed, the air pressure against the board 118 is such as to turn it, thereby disconnecting the finger 117 from the latch and permitting the spring 116 to move thelatch out of the recess 114 so as to permit the pendulum to move relatively to the flying machine.

The flyin machine to which the e uilibratin mechanism is shown as applied 15 of the se f-propelled and self-controlled type for carryinga charge of explosive mixture and projectiles to a predetermined point where it is detonated. One feature of the invention accordingly is .to ada t the main pendulum, by which the gui mg devices are controlled to maintain the equlhbrlum or stability of the flying machine while it battery 129 is located,:so that the latter no longer energizes the solenoid 130. Thereupon ahammer 131 normally held up by the solenoid 13() drops upon a cap or fuse i1'32 detonating' the charge of explosive mixure.

Although in the illustrated embodiment of the invention the equilibrating mechanism hasbeen shown as applied to a selfpropelled and self-controlled flying machine, it will be understood that the cquilibrating mechanism of the present invention is equally. well adapted for application to other types of mac ines than flying machines and in particular to a flying machine which is primarily controlled by an aeronaut.

Having thus described the invention what is claimed is:

1. An equilibrating mechanism for flying machines comprising a guiding device, a lever connected with the guiding device, a main pendulum normally disconnected .from the lever, a magnet carried by the pendulum, an armature carried by the lever, a battery in a circuit normally open, and an auxiliary pendulum adapted when the equilibrium of the flying machine is disturbed to close the circuit so as to enerize the magnet to turn the lever and thereby impart a primary restoring movement to the guiding device, the energizing of the magnet servin to connect the lever with the main pendulum so that the guiding device is thereafter turned proportionately to the change in the angular relation between the mam pendulum and the flying machine,

2.- An equilibrating mechanism for flying.

machines comprising guiding devices, operating means therefor, a main pendulum normally disconnected from the guiding device operatin means, but which when connected therewiti serves to turn the guiding devices proportionately to a change in the angular relation between the mam pendulum and the flying machine, and an auxiliary pendulum for imparting a primary restoring movement to the guiding devices when thee uilibrium of the flying machine is disturbed.

3. An equilibrating mechanism for flying machines comprising guiding devices, a pen dulum normally disconnected from the guiding devices, an auxiliary device, and means through which when the equilibrium of the rimary restoring machine is disturbed a movement is imparted to t 1e guiding devices throu h the action of the auxiliary device and t iey are thereby connected with the pendulum to be thereafter moved propor- 'tionately to the amount of angular change between the pendulum and the flying machine.

4. An equilibrating machines comprising atin" means therefor, malfy mechanism for flying guiding devices, opera main pendulum nor disconnected from the guiding device operating means, an auxiliary pendulum,

and asolenoid interposed between the main pendulum and the guiding device operating means ada ted to he energized through the action of the auxiliary pendulum to connect the two when the equilibrium of the flying machine is disturbed.

5. An equilibrating mechanism for flying machines comprising a horizontal ru dcr, operating means therefor, a main pendulum, an auxiliary pendulum, and means for causing the rudder operating means to move the rudder when the auxiliary pendulum changes its angular relation with the flying machine to thereby connect the main pendulum with the rudder operating means so as to turnthe rudder pro ortionately to thechange in the angular re ation between-the main pendulum and the longitudinal ax s of the flying machine.

6. An equilibrating mechanism for flying machines comprising lateral rudders or.

ailerons located on opposite sides of the flying machine, a system of levers connected with the ailerons in such manner that when the levers are turned in the same direction the ailerons on one side of the machine are moved in one direction and the ailerons on the other side of the machine aremoved in the opposite direction, a main endulum normally disconnected from the evers, an auxiliary pendulum and means through which the auxiliary pendulum acts when the lateral equilibrium cit the machine is disturbed to impart a primary restoring movement to the ailerons and to thereby connect the main pendulum with the levers.

7. An equilibrating mechanism for flying machines comprising guiding devices, a main pendulum, means interposed between the main pendulum and the guiding devices throu h which the guiding devices are turned proportionately to the change in angular relation between the main pendulum and the flying machine, a mounting for the main pendulum so that it may swing both fore and aft and laterally, magnets carried by the main pendulum for connecting it with the means interposed between it and the guiding devices, and an auxiliary pendulmn acting when the equilibrium of the ma- Zhine is disturbed to close a circuit and hereby energize certain of the magnets.

8. An equilibrating mechanism for flying machines comprisin a pendulum, means for holding the penduFum in rigid connection with the flying machine, and means for automatically releasing the holding means when the fl ing machine has attained a redetermine speed whereupon the pen ulum is free to move relatively to the flying machine.

9. An equilibrating mechanism for flying machines comprising a guiding device, operatin means therefor, a pendulum for contro mg the guiding device 0 eratin means, means for holding the pendulum an the flying machine immovable relatively and means for automatically releasing the hold.- ing means when the flying machine attains a predetermined speed.

10. An equilibrating mechanism for flying machines comprising a guiding device, operating means therefor, a endulum for controlling the guiding device 0 crating means, a latch for holding the pend iilum in rigid connection with the flying machine, and means for automatically disconnecting the latch from the pendulum when the flying machine has attained a predetermined speed. p

11. An equilibrating mechanism for flying machines comprising means operable after a time interval followin -the displacement of the flying machine iirom a condition of equilibrium to restore the machine to equilibrium, and means tending to restore the machine to'equilibrium before the operation of the said restoring means.

12. An equilibrating mechanism for flyin machines comprisin a guiding device, a refirtively heavy pendu um adapted to operate u on the guiding device after a time interval following the displacement of the machine from a condition of equilibrium to restore the machine to equilibrium and a.

relatively light pendulum adapted to open I ate upon the guiding device to tend to restore the machine to equilibrium before the operation of the relatively heavy pendulum.

13. An equilihratin mechanism for tlying machines comprisin a guiding device, a relatively heavy pendu um ada ted toppcrate upon the guiding device a ter a, time interval following the displacement of the machine flOllL a condition of equilibrium to restore the machine to equilibrium and a relatively light pendulum adapted to operate upon the guiding device to tend to re store the machine to equilibrium before the operation of the relatively heavy pendulum, and means whereby the operation of the ielatively light pendulum renders the relatively heavy pendulum operative.

14. An equilibrating mechanism for flyin machines having, in combination, a. guiding device, means operable upon a dis- 2 placement of the flying machine from a condition of equilibrium for controlling the position of the guiding device in accordance with the degree of displacement of the machine from equilibrium to effect a. restora- 2 tion of the machine to equilibrium with a force which gradually decreases to zero as the equilibrium of the machine becomes gradually restored, and means for compensatin for the lack of control over the uid- 3 ing evice during the displacement o the machine from equilibrium to the predetermined degree of displacement.

ERASTUS E. WINKLEY 

